Satellite and load simulator based on software definition

Abstract

The invention discloses a satellite and load simulator based on software definition. The satellite and load simulator comprises a case, a back plate and a cooling fan tray which are fixedly connected to the case, a general function board card and a power card which are installed on the front face of the back plate, and a management IO card and a back plate exchange card which are installed on the back face of the back plate. The general function board card, the power supply card, the cooling fan tray, the management IO card and the backboard exchange card are electrically connected through the backboard; an embedded operating system consistent with a simulated real object load runs on the universal function board card, and the universal function board card is provided with a CPU (Central Processing Unit) or an FPGA (Field Programmable Gate Array) processor; the backboard exchange card is used for realizing signal interconnection and protocol data packet exchange between the universal function board cards and between different types of interfaces; and the management IO card is used for connecting the satellite and load simulator with an external host. According to the invention, the volume of the satellite and the load simulator can be effectively reduced, the cost is reduced, and the reuse capability of the satellite and the load simulator is improved through a software definition mode.

Description

Technical Field

[0001] The present invention relates to the technical field of simulators, and in particular to a satellite and payload simulator based on software definition. Background Art

[0002] During the development and production of satellite payloads (stand-alone), it is necessary to use other equipment and boards to build a payload simulator. The purpose is to simulate the logical functions and interface electrical characteristics of other payloads, communicate and interact with the developed payload data, and verify whether the functional performance of its own payload meets the requirements; during the whole satellite joint debugging and assembly testing process, it is necessary to use a payload simulator to replace the function of a certain payload when it is not ready or fails, to ensure the smooth progress of the whole satellite test and assist in troubleshooting the cause of the fault; during the satellite system testing process, it is necessary to use a satellite simulator to simulate multiple satellites and complete relevant system-level tests together with the physical satellite.

[0003] However, existing load simulators have certain defects in architectural design, processing performance, configuration capability, communication performance and verification capability.

[0004] Architectural design flaws: Traditional satellite or payload simulators are mostly based on standard industrial computer architectures such as CPCI / PXI / PXIe / VPX. These architectures utilize an industrial computer chassis, controller, and specialized function boards. The chassis provides the entire system's power supply, backplane, and cooling system; the controller, like a computer mainframe, houses a general-purpose processor; and specialized function boards include but are not limited to RS232 communication cards, RS422 / 485 communication cards, LVDS interface cards, Ethernet port cards, SerDes cards, and CAN cards. Typically, each industrial computer can only simulate one payload or satellite. This results in a bulky simulator, high power consumption, and extremely high cost.

[0005] ●Processing performance defects: Since this type of simulator adopts the industrial computer structure, it must be installed with a controller that serves as the brain of the industrial computer. However, the size and heat dissipation space of the controller are restricted by standards, and the performance of the processor integrated on it is usually low, which cannot perform complex data processing. The software of the new satellite test system usually runs on a remote host, which is responsible for processing the upper-level data. The test equipment itself does not need to perform local processing, and the local processor becomes redundant at this time.

[0006] ● Configuration capability defects: The external IO card corresponding to the functional board used by this simulator needs to be installed on the back of the chassis, corresponding one-to-one with the position of the functional board. As a result, the functional board usually needs to be inserted into a designated slot system to work properly. The slot position cannot be changed at will, and the layout cannot be optimized according to the output of the board, which limits the flexible configuration capability of the simulator.

[0007] ●Communication performance defects: The functional boards used in this simulator can only communicate with the host or other functional boards through a specific PCI or PCI-e bus. It is impossible to directly use the same communication interface as the physical payload to simulate the actual communication effect, which greatly reduces the verification effect. Moreover, the communication data between functional boards must flow through the root complex of the PCI or PCI-e bus (usually the processor on the controller). Therefore, its actual available throughput is also limited by the interface bandwidth, the processing power of the controller and the capabilities of the driver.

[0008] Verification Capabilities: The functional boards in this type of simulator typically only have signal acquisition and action execution capabilities. The boards themselves lack data processing capabilities, and the vast majority of data processing is performed on the controller. The controller typically runs a desktop version of Windows or Linux, which differs significantly from the embedded real-time operating systems (RTOS) such as VxWorks, FreeRTOS, or SylixOS commonly used on actual satellites. Consequently, data processing software must be rewritten, making it virtually impossible to reuse existing payload code. This makes it impossible to verify the data processing processes of actual payloads and satellites. This is one reason these simulators are large and can only simulate a single payload or satellite.

[0009] In summary, traditional satellite and payload simulators are increasingly unable to meet actual needs and have the following problems.

[0010] 1) Traditional satellite and payload simulators are large in size, and the hardware boards required to build satellite and payload simulators are diverse and have single functions.

[0011] 2) There are huge differences in hardware between satellites and payload simulators with different functions. Each time a new simulator is designed, the hardware needs to be replaced, resulting in poor reusability.

[0012] 3) Traditional satellite and payload simulators cannot simulate the communication process and communication capabilities of real satellites and payloads, and cannot truly verify the actual communication effects.

[0013] 4) The controllers on traditional satellite and payload simulators cannot reuse the data processing codes of actual satellites and payloads, and cannot truly verify the data processing process of the actual objects.

[0014] 5) Traditional satellite and payload simulators have poor flexible configuration capabilities, and the board positions cannot be flexibly adjusted. Once inserted incorrectly, it may cause the simulator to malfunction at best, or even damage the simulator or even the payload being measured. Summary of the Invention

[0015] In response to the above problems, the present invention discloses a satellite and payload simulator based on software definition, which can effectively reduce the size of the satellite and payload simulator, reduce costs, and improve the reusability of the satellite and payload simulator through software definition.

[0016] To achieve the above objectives, the technical solution of the present invention includes the following contents.

[0017] A software-defined satellite and payload simulator, characterized in that the satellite and payload simulator comprises: a chassis (10), a backplane (60) and a cooling fan tray (70) fixed to the chassis (10), a universal function board (20) and a power supply card (50) installed on the front of the backplane (60), and a management IO card (80) and a backplane switch card installed on the back of the backplane (60);

[0018] The universal function board (20), the power supply card (50), the cooling fan tray (70), the management IO card (80) and the backplane switch card are electrically connected via the backplane (60);

[0019] The universal function board (20) runs an embedded operating system consistent with the simulated physical load and has a CPU processor or an FPGA processor;

[0020] The backplane switching card is used to realize signal interconnection and protocol data packet exchange between universal function boards (20) and between different types of interfaces;

[0021] The management IO card (80) is used for connecting the satellite and payload simulator with an external host.

[0022] Furthermore, the chassis (10) has a PCB guide groove (13), a cooling fan tray guide groove (14) and a backplane mounting plane (15); wherein the PCB guide groove includes: a function board slot and a power supply card slot.

[0023] Furthermore, the universal function board (20) is electrically connected to the backplane (60) via a first connector, and the model, spacing and signal definition of the first connector are different from those of the connector of a standard PXIe board.

[0024] Furthermore, when the function or performance of the general function board card cannot meet the requirements, the satellite and payload simulator also includes: a dedicated function board card (40); wherein the dedicated function board card (40) is electrically connected to the backplane (60) through a second connector, and the model, spacing and signal definition of the second connector are different from those of the first connector and the connector of the standard PXIe board card.

[0025] Furthermore, the operation and update process of the embedded operating system includes:

[0026] Running a boot program to initialize the universal function board (20), and loading and starting an embedded operating system;

[0027] Starting an application program directly related to the function of the universal function board (20) to implement the software definition of the function of the universal function board (20);

[0028] Start the update service, and when the update service monitors the update push message, determine in turn whether the boot program, operating system and application need to be updated, perform integrity check of the new version of the software, and update the corresponding application online.

[0029] Furthermore, the satellite and payload simulator further comprises an IO expansion card (30); wherein the IO expansion card (30) is electrically connected to the universal function board card (20) and is used to expand the external interface of the universal function board card (20).

[0030] Furthermore, the backplane switching card has a CPU processor and an FPGA processor, and when all port line rates are greater than a set value, data exchange is performed in the FPGA processor, and the CPU processor calculates the switching path and specifies the switching strategy.

[0031] Furthermore, a power management unit is provided on the back panel (60), and the functions of the power management unit include:

[0032] Power off and power on the entire machine according to remote control instructions and predetermined rules;

[0033] Powering off and powering on a designated universal function board (20) according to remote control instructions and predetermined rules;

[0034] Detect AC voltage zero point;

[0035] Collect, summarize and analyze the power consumption of the general function board (20), management IO card, backplane interaction card and the whole machine;

[0036] The rotation speed of the fan in the heat dissipation fan tray (70) is controlled.

[0037] Furthermore, the power card (50) provides the backplane (60) with one normally closed standby power supply and multiple controlled power supplies; wherein the normally closed standby power supply is used to supply power to the standby circuits of the power management unit, the universal function board (20), the management IO card (80) and the backplane switch card, and the controlled power supply is controlled by the power management unit.

[0038] Furthermore, the management IO card (80) provides a management network port, a service network port and a terminal debugging serial port; wherein the management network port is connected to the processor of the backplane power management unit; the terminal debugging serial port is connected to the processor of the power management unit to realize the bottom-level control and status monitoring of the power management unit; and the service network port is connected to the processor of the backplane switch card.

[0039] Compared with the prior art, the present invention has the following positive effects:

[0040] The software-defined satellite and payload simulator of the present invention can be used as a simulator to simulate a certain payload or even an entire satellite, and can also be used as a test system to test the payload and satellite in real life.

[0041] The software-defined satellite and payload simulator of the present invention can simulate a single payload or even an entire satellite using a small number of boards. The overall size is small, and the main hardware can be universalized. The function of the board can be changed by updating the software on the board, and the board can be reused, thereby realizing the transformation of the simulator function and reducing repeated investment.

[0042] The communication interface used on the function board of the software-defined satellite and payload simulator of the present invention is basically consistent with the simulated object, and can verify the actual communication effect of the object.

[0043] The present invention is based on a software-defined satellite and the operating system running on the functional board of the payload simulator is consistent with the simulated object, and the data processing code running is basically consistent with the actual object, which can truly verify the data processing process of the actual object.

[0044] The positions of the function boards of the satellite and payload simulator defined by the software of the present invention can be flexibly adjusted without relying on the slot positions.

[0045] The present invention does not require an additional controller on the software-defined satellite and payload simulator, and only requires the backboard to have basic data aggregation, distribution and transmission functions. The processing function of the test data is mainly completed by the remote host. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 The overall structure diagram of the software-defined satellite and payload simulator.

[0047] Figure 2 Basic structure diagram of the chassis.

[0048] Figure 3 Diagram showing the difference in connector spacing between standard PXIe boards and simulator function boards.

[0049] Figure 4Schematic diagram of the software operation and update process on the functional board of the software-defined satellite and payload simulator.

[0050] Figure 5 Schematic diagram of the front of the back panel.

[0051] Figure 6 Schematic diagram of the back panel.

[0052] Figure 7 Basic circuit structure diagram of the power management unit.

[0053] Figure 8 Schematic diagram of the basic circuit structure and data flow of the backplane switch card.

[0054] Figure 9 Basic structure diagram of the power card.

[0055] Figure 10 Diagram of the basic structure of the cooling fan tray.

[0056] Figure 11 Example diagram of a satellite and payload simulator. DETAILED DESCRIPTION

[0057] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described below with reference to specific embodiments and drawings.

[0058] The software-defined satellite and payload simulator discussed in this design is limited to simulating the data communication and data processing processes of the satellite and payload. The specific signal acquisition and execution mechanisms need to be implemented by the simulator in combination with corresponding peripheral components.

[0059] The software-defined satellite and payload simulator has an external network interface and can be connected to the semi-physical satellite simulation system for semi-physical simulation.

[0060] The software-defined satellite and payload simulator can be used as both a simulator and a test system. It can be used as a simulator for a satellite payload (also called a "standalone") or an entire satellite, or it can be used as a test system to test a satellite payload or even the entire satellite.

[0061] I. Overall Plan

[0062] The software-defined satellite and payload simulator consists of at least eight components: chassis, function boards (including general function boards and special function boards), IO expansion cards, backplanes, backplane switch cards, power cards, cooling fan trays, and management IO cards. Figure 1 As shown in the figure For the chassis, It is a general function board. For IO expansion card, It is a dedicated function board. For the power card, Backplane (backplane switch card is installed later, which is blocked and not shown). For the cooling fan tray, To manage IO cards.

[0063] In the software-defined satellite and payload simulator, the IO expansion card 30, power card 50, cooling fan tray 70 and management IO card 80 are pure hardware and have no software functions; the general function board card 20, the dedicated function board card 40, the backplane switch card and the power management unit on the backplane are components with software functions, and their functions can be redefined by online updating of the loaded software according to different business needs; the power card can be replaced with different specifications according to different load requirements.

[0064] In software-defined satellite and payload simulators, all components except the backplane are pluggable. Except for the backplane switch card, other boards (including power cards) support hot plugging. The system can automatically identify the insertion and removal operations of the boards and control the power on and off of the boards according to predetermined rules.

[0065] 2. Chassis

[0066] The software-defined chassis for the satellite and payload simulator provides mounting space and physical protection for other components. The chassis's basic structure follows the PXIe standard for mechanical structure, chassis components, and dimensions, eliminating the need for custom components. The chassis' bottom features guide slots for mounting the cooling fan tray. To minimize overall size, a 3U chassis structure was specified.

[0067] The front slots of the chassis for software-defined satellite and payload simulators include two types: function board slots and power card slots. The function board slots are located on the left side of the chassis, providing at least 7 standard slots and a maximum of 15 standard slots. The power card slot is located on the far right side of the chassis, with 3 standard slots reserved. The back only provides an AC power socket and a management IO card slot. The basic structure of the chassis is as follows: Figure 2 As shown in the figure For the chassis shell, For the chassis metal frame, For PCB guide groove, It is the guide groove for the cooling fan tray. The (horizontally highlighted strip area) is the back panel mounting surface.

[0068] 3. Functional board

[0069] The functional boards of software-defined satellites and payload simulators use the same board type, size structure, and locking mechanism as the 3U standard PXIe boards. However, the connector types, connector spacing, and signal definitions are significantly different from those of standard PXIe boards, creating an anti-mock feature with standard PXIe boards to effectively prevent incorrect insertion. Figure 3 The figure below is a diagram showing the difference in connector spacing between standard PXIe boards and simulator function boards. The right side shows the connector appearance and spacing of the standard PXIe board, and the left side shows the connector appearance and spacing of the simulator function board. Figure 3 As can be seen, the board connector specifications and connector spacing defined by this simulator are significantly different from those of standard PXIe boards, ensuring that the two boards are incompatible with each other and will not be plugged in incorrectly.

[0070] The hardware of the general function board based on software-defined satellite and payload simulator is exactly the same. It has two types of processors: CPU and FPGA. The specific functions are defined and modified by software, and support online dynamic updates. A single card can simulate one payload or even one satellite, and is marked with a blue triangle on the panel.

[0071] The functional boards of the software-defined satellite and payload simulator run an embedded operating system that is consistent with the physical payload being simulated, support online updates, and can restore the software operating environment of the physical payload to the greatest extent possible; the data processing code that is run is basically consistent with the physical payload, which not only reduces repeated development but also can truly verify the data processing process of the physical payload. Most common industrial control boards only have interface conversion functions and do not have their own software; a small number of industrial control boards have their own software functions, but their functions are fixed and do not support online updates, let alone redefinition of their functions. The functional boards mentioned in the present invention all run functional software, and their functions can be redefined by updating the software online.

[0072] The software operation and update process on the function board of the software-defined satellite and payload simulator is as follows: Figure 4As shown in the figure, the process within the bold dashed box represents the same software execution flow as traditional industrial control boards with software functions. The process within the undashed box represents the unique process for functional boards in software-defined satellites and payload simulators, which implements function redefinition and online updates. After the system is powered on, the processor first runs the bootloader, which initializes the board and loads and starts the operating system. The operating system then initiates two processes: one is the application program directly related to the board's functions, which performs the required functions. Unlike traditional industrial control boards, these applications can have multiple copies, running different applications according to different instructions, thus achieving software-defined board functions. The other is the update service, which is responsible for online updates of all software on the board. The operating system mentioned here is the same embedded operating system as the actual device being simulated, and the data processing code used in the application program is essentially the same as the actual code. The update service periodically checks for update push notifications. If no update is available, it continues to listen for update push notifications. If an update is available, it determines whether the bootloader, operating system, and application program need to be updated, performs an integrity check on the new software version, and then updates the corresponding programs online. After all updates are complete, the system determines whether the updates need to be applied immediately. If not, it continues to listen for update push notifications. If so, it determines whether a system reboot is necessary. If not, it restarts only the application, and the new software is applied after the next reboot. Otherwise, it restarts the entire operating system and applies the new software directly.

[0073] The general function board of the software-defined satellite and payload simulator integrates commonly used on-board interfaces in hardware, such as RS232, RS422 / 485, CAN, LVDS, network port, SerDes and IO pins. The pin positions of these physical signals are fixed, but their logical functions can be defined and modified through software. For example, RS422 / 485 can be set to synchronous mode and asynchronous mode through software, LVDS can be set to synchronous serial port, asynchronous serial port and SpaceWire interface through software, and SerDes can be set to SATA, PCI-e and SGMII and other high-speed interface types through software. This ensures that the interfaces used on the general function board are basically consistent with the actual objects, and can verify the communication effect of the simulated object to the greatest extent.

[0074] Software-defined, specialized function boards for satellites and payload simulators are used for additional customization when the functionality or performance of general-purpose function boards falls short of requirements. While they share the same form factor and backplane connector types as general-purpose function boards, their connector spacing and signal definitions differ from those of general-purpose function boards and standard PXIe boards. These boards are distinguished by a green triangle on the front panel, ensuring a seamless interface between them. The specific functions of these boards are also defined and modified by software, supporting online dynamic updates.

[0075] Two types of temperature sensors need to be installed uniformly on the functional boards, backplanes, power cards and backplane switch cards of software-defined satellites and payload simulators. One is a PCB onboard temperature sensor, and the other is a lead-type sensor. They are placed at the highest temperature point on the PCB surface and the highest possible temperature point of the functional board as a whole (such as the processor housing or power module heat sink position). The sensor information is read by the power management unit of the backplane and cannot be directly accessed by the board itself.

[0076] For software-defined satellites and payload simulators, the functional boards, backplanes, power cards, and backplane switch cards must all be equipped with additional EEPROMs of specified models. The EEPROMs record information such as the board type, hardware version number, and unique serial number. The memory contents can only be read and modified by the backplane's power management unit.

[0077] The functional boards of software-defined satellite and payload simulators can change slot positions at will. The system identifies the board type and its defined payload function through the unique serial number stored on the functional board or the telemetry information uploaded by the functional board. This ensures that the board function is independent of its position, facilitates board arrangement, optimizes layout, and prevents system anomalies or test device failures caused by incorrect board position insertion.

[0078] The function boards for software-defined satellites and payload simulators can be equipped with heat sinks. These heat sinks must provide mounting locations for cooling fans, and the PCB must provide power sockets for these fans. A cooling fan can be installed during single-card debugging, but it is not included when installed in the chassis.

[0079] 4.IO expansion card

[0080] The function boards for software-defined satellites and payload simulators have simple indicator lights on their panels, providing information such as power, alarms, errors, and operating status, along with a local reset button. If the function boards require external interfaces, these are connected via an additional IO expansion card. The IO expansion card is installed and fixed alongside the function board itself, but does not plug into the backplane. It can occupy up to two standard slots, and the expanded interfaces are connected through the front panel of the chassis.

[0081] 5. Back panel

[0082] The backplane of the software-defined satellite and payload simulator provides installation sockets, power supplies, and interconnection channels for various other boards. Functional boards, cooling fan trays, and power cards are installed on the front of the backplane, while management IO cards and backplane switch cards are installed on the back of the backplane. Figure 5 and Figure 6 As shown in the figure It is a universal function board socket. It is a dedicated function board socket. For the power card socket, For the cooling fan tray socket, For AC power socket, Backplane power management unit, To manage IO card sockets, Backplane switch card socket.

[0083] The backplane of the software-defined satellite and payload simulator is equipped with a power management unit. The power management unit has an Ethernet interface, supports network wake-up, and the main power switch supports local control and remote control; it has a power control circuit, which can power on and off the entire machine according to remote control instructions and predetermined rules, and can also power on and off the specified board; it has a zero-crossing detection circuit, which can detect the zero point of the AC voltage. The software performs various power switching actions at the zero point of the AC voltage, which can reduce the impact of load changes on the power grid and power circuits; it has an analog acquisition circuit, which can collect, summarize and analyze the power consumption of each board and the entire machine. In addition to being transmitted as a telemetry measurement to the satellite computer and the host computer, it also serves as an input parameter for fan speed control; it has a fan control and temperature sensor control circuit, which can read the temperature values ​​of the temperature sensors on various other components, and control the fan speed in combination with the power consumption of the board, which can reduce fan noise while ensuring effective heat dissipation. The basic circuit structure of the power management unit is as follows: Figure 7 shown.

[0084] The backplane of the software-defined satellite and payload simulator supports the aggregation of functional board signals and connects the aggregated signals to the corresponding connector pins of the backplane switch card.

[0085] The backplane of the software-defined satellite and payload simulator has the function of protecting and filtering the input industrial frequency AC power, ensuring that the voltage input to the power card does not exceed the specified range.

[0086] 6. Backplane switch card

[0087] The backplane switching card based on software-defined satellite and payload simulator is installed on the back of the backplane to realize signal interconnection and protocol data packet exchange between different functional boards and different types of interfaces. The interconnection relationship and exchange strategy can be dynamically modified by software. The backplane switching card needs to have two types of processors, CPU and FPGA, and it is stipulated that data exchange with a line rate of ≥10Mbps for all ports must be performed in FPGA. The original data does not need to pass through the CPU. The CPU only needs to calculate the exchange path and specify the exchange strategy, which can effectively ensure the data throughput between boards. Its basic circuit structure and data flow are as follows: Figure 8 As shown in the figure, the interface circuit completes the high-, medium- and low-speed interface signal shaping. The interface protocol adaptation logic inside the FPGA completes the interface protocol identification and protocol data unpacking. The interface protocol exchange logic completes the protocol data packet exchange between interfaces. The processor interaction logic completes the interaction with the CPU, obtains the exchange path and exchange strategy sent by the CPU and reports the telemetry information. The CPU uses the remote control and telemetry interface to communicate with the satellite computer.

[0088] The backplane switching card of the software-defined satellite and payload simulator only performs protocol processing on the communication messages, and does not process the payload data in the messages. All payload data is processed by the functional board or external host computer.

[0089] 7. Power card

[0090] The power card for the satellite and payload simulator, based on software-defined inputs, draws the mains voltage from the backplane, providing the backplane with a normally closed standby power supply and multiple controlled power supplies. The normally closed standby power supply is used to power the backplane power management unit and the standby circuits of other boards, while the controlled power supply is controlled by the backplane power management unit. The power card panel provides power, output, and protection indicators, and provides local soft switching. The basic structure of the power card is as follows: Figure 9 shown.

[0091] The power supply card for the software-defined satellite and payload simulator occupies 2 standard slots by default and can occupy up to 3 standard slots.

[0092] 8. Cooling fan tray

[0093] The fan array is arranged in the cooling fan tray of the software-defined satellite and payload simulator. The fan itself supports speed regulation and speed measurement. Each fan can independently control the start and stop and speed of each fan. The backplane power management unit performs real-time partition control based on the collected temperature and power consumption data, thereby achieving the purpose of controlling the temperature in the chassis while reducing the noise of the entire machine. Its internal basic structure is as follows Figure 10 As shown, For fan array, For the fan control board, Position the guide pins for the tray, Metal frame for pallet.

[0094] The fan speed control strategy for the cooling fan tray of the software-defined satellite and payload simulator can also be redefined through software. By modifying the software configuration and control algorithm of the backplane power management unit online, the chassis temperature and noise control requirements for different application scenarios can be met.

[0095] 9. Manage IO Cards

[0096] The management IO card based on software-defined satellite and payload simulator is used to connect the chassis to the external host, providing 1 management network port and 1 business network port. The management network port is connected to the processor of the backplane power management unit, and the business network port is connected to the processor of the backplane switch card.

[0097] The management IO card of the software-defined satellite and payload simulator also provides a terminal debugging serial port through an RJ45 connector, which is connected to the processor of the backplane power management unit. It uses the same signal definition as the commercial router terminal serial port to implement the lowest-level control and status monitoring of the backplane power management unit.

[0098] Figure 11 This is an example of a satellite and payload simulator designed according to the principles of the present invention. This simulator implements all the functions mentioned herein and can accommodate up to six general-purpose function boards and one dedicated function board. Practical use has proven that the satellite and payload simulator design method proposed in this invention is reasonable and feasible, effectively reducing the size and cost of the satellite and payload simulator, and increasing its reusability through software-defined methods.

[0099] While specific embodiments of the present invention have been disclosed for illustrative purposes, intended to facilitate understanding and implementation of the present invention, those skilled in the art will appreciate that various substitutions, variations, and modifications are possible without departing from the spirit and scope of the present invention and the appended claims. Therefore, the present invention should not be limited to the disclosure of the preferred embodiments, and the scope of protection claimed in the present invention shall be determined by the scope of the claims.

Claims

1. A software-defined satellite and payload simulator, characterized in that: The satellite and payload simulator comprises: a chassis (10), a backplane (60) and a cooling fan tray (70) fixed to the chassis (10), a universal function board (20) and a power supply card (50) installed on the front of the backplane (60), and a management IO card (80) and a backplane switch card installed on the back of the backplane (60); The universal function board (20), the power supply card (50), the cooling fan tray (70), the management IO card (80) and the backplane switch card are electrically connected via the backplane (60); The universal function board (20) runs an embedded operating system consistent with the simulated physical load and has a CPU processor or an FPGA processor; The backplane switching card is used to realize signal interconnection and protocol data packet exchange between universal function boards (20) and between different types of interfaces; The management IO card (80) is used for connecting the satellite and payload simulator with an external host.

2. The software-defined satellite and payload simulator according to claim 1, characterized in that: The chassis (10) has a PCB guide groove (13), a cooling fan tray guide groove (14) and a backplane mounting plane (15); wherein the PCB guide groove includes: a function board slot and a power supply card slot.

3. The software-defined satellite and payload simulator according to claim 1, wherein: The universal function board (20) is electrically connected to the backplane (60) via a first connector, and the model, spacing and signal definition of the first connector are different from those of the connector of a standard PXIe board.

4. The software-defined satellite and payload simulator according to claim 3, wherein: When the function or performance of the general function board card cannot meet the requirements, the satellite and payload simulator further includes: a dedicated function board card (40); wherein the dedicated function board card (40) is electrically connected to the backplane (60) through a second connector, and the model, spacing and signal definition of the second connector are different from those of the first connector and the connector of the standard PXIe board card.

5. The software-defined satellite and payload simulator according to claim 1, wherein: The operation and update process of the embedded operating system includes: Running a boot program to initialize the universal function board (20), and loading and starting an embedded operating system; Starting an application program directly related to the function of the universal function board (20) to implement the software definition of the function of the universal function board (20); Start the update service, and when the update service monitors the update push message, determine in turn whether the boot program, operating system and application need to be updated, perform integrity check of the new version of the software, and update the corresponding application online.

6. The software-defined satellite and payload simulator according to claim 1, wherein: The satellite and payload simulator further comprises an IO expansion card (30); wherein the IO expansion card (30) is electrically connected to the universal function board card (20) and is used to expand the external interface of the universal function board card (20).

7. The software-defined satellite and payload simulator according to claim 1, wherein: The backplane switching card has a CPU processor and an FPGA processor. When all port line rates are greater than a set value, data exchange is performed in the FPGA processor, and the CPU processor calculates a switching path and specifies a switching strategy.

8. The software-defined satellite and payload simulator according to claim 1, wherein: The back panel (60) is provided with a power management unit, and the functions of the power management unit include: Power off and power on the entire machine according to remote control instructions and predetermined rules; Powering off and powering on a designated universal function board (20) according to remote control instructions and predetermined rules; Detect AC voltage zero point; Collect, summarize and analyze the power consumption of the general function board (20), management IO card, backplane interaction card and the whole machine; The rotation speed of the fan in the heat dissipation fan tray (70) is controlled.

9. The software-defined satellite and payload simulator according to claim 8, characterized in that: The power card (50) provides the backplane (60) with one normally closed standby power supply and multiple controlled power supplies; wherein the normally closed standby power supply is used to supply power to the standby circuits of the power management unit, the universal function board (20), the management IO card (80) and the backplane switch card, and the controlled power supply is controlled by the power management unit.

10. The software-defined satellite and payload simulator according to claim 8, characterized in that: The management IO card (80) provides a management network port, a service network port and a terminal debugging serial port; wherein the management network port is connected to the processor of the backplane power management unit; the terminal debugging serial port is connected to the processor of the power management unit to realize the bottom-level control and status monitoring of the power management unit; and the service network port is connected to the processor of the backplane switch card.

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